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WO2008111957A8 - Stator assembly including bleed ports for turbine engine compressor, turbine engine compressor with such an assembly, segment of such an assembly, and corresponding operating method - Google Patents

Stator assembly including bleed ports for turbine engine compressor, turbine engine compressor with such an assembly, segment of such an assembly, and corresponding operating method Download PDF

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Publication number
WO2008111957A8
WO2008111957A8 PCT/US2007/019980 US2007019980W WO2008111957A8 WO 2008111957 A8 WO2008111957 A8 WO 2008111957A8 US 2007019980 W US2007019980 W US 2007019980W WO 2008111957 A8 WO2008111957 A8 WO 2008111957A8
Authority
WO
WIPO (PCT)
Prior art keywords
stator
assembly
turbine engine
engine compressor
vanes
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/US2007/019980
Other languages
French (fr)
Other versions
WO2008111957A2 (en
WO2008111957A3 (en
Inventor
Sachin V Damle
Bachar Adjan
Jerry Mar Philip Fregoe
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Solar Turbines Inc
Original Assignee
Solar Turbines Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Solar Turbines Inc filed Critical Solar Turbines Inc
Priority to GB0904122A priority Critical patent/GB2454434B/en
Priority to DE112007002131T priority patent/DE112007002131T5/en
Priority to CN2007800383505A priority patent/CN101595287B/en
Publication of WO2008111957A2 publication Critical patent/WO2008111957A2/en
Publication of WO2008111957A3 publication Critical patent/WO2008111957A3/en
Anticipated expiration legal-status Critical
Publication of WO2008111957A8 publication Critical patent/WO2008111957A8/en
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A stator assembly (34) for a turbine engine (10) is disclosed. The stator assembly (34) has a stator support ring (42), a plurality of stator vanes (40) protruding radially inwardly from the stator support ring (42), and at least one bleed port (48) disposed on the stator support ring (42) in a static high pressure region (50) between at least two adjacent stator vanes (40a, 40b) of the plurality of stator vanes (40). The at least one bleed port (48) defines an oblong profile. The profile includes a first end (48a) terminating near a leading edge (52) of a first stator vane (40a) of the at least two adjacent stator vanes (40a, 40b), and a second end (48b), substantially opposed from the first end (48a), terminating near a trailing edge (54) of a second stator vane (40b) of the at least two adjacent stator vanes (40a, 40b). The profile is concave toward a suction sidewall (58) of the stator vane second (40b) of the at least two adjacent stator vanes (40a, 40b).
PCT/US2007/019980 2006-09-14 2007-09-14 Stator assembly including bleed ports for turbine engine compressor, turbine engine compressor with such an assembly, segment of such an assembly, and corresponding operating method Ceased WO2008111957A2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB0904122A GB2454434B (en) 2006-09-14 2007-09-14 Stator assembly including bleed ports for turbine engine compressor
DE112007002131T DE112007002131T5 (en) 2006-09-14 2007-09-14 Stator arrangement with removal openings for a compressor of a turbine engine, turbine engine compressor with such an arrangement, segment of such an arrangement and corresponding method of operation
CN2007800383505A CN101595287B (en) 2006-09-14 2007-09-14 Stator assembly including bleed ports for turbine engine compressor, turbine engine compressor with assembly and its corresponding operating method

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US84439706P 2006-09-14 2006-09-14
US60/844,397 2006-09-14
US11/898,604 2007-09-13
US11/898,604 US8292567B2 (en) 2006-09-14 2007-09-13 Stator assembly including bleed ports for turbine engine compressor

Publications (3)

Publication Number Publication Date
WO2008111957A2 WO2008111957A2 (en) 2008-09-18
WO2008111957A3 WO2008111957A3 (en) 2008-11-06
WO2008111957A8 true WO2008111957A8 (en) 2009-08-06

Family

ID=39565518

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2007/019980 Ceased WO2008111957A2 (en) 2006-09-14 2007-09-14 Stator assembly including bleed ports for turbine engine compressor, turbine engine compressor with such an assembly, segment of such an assembly, and corresponding operating method

Country Status (5)

Country Link
US (1) US8292567B2 (en)
CN (1) CN101595287B (en)
DE (1) DE112007002131T5 (en)
GB (1) GB2454434B (en)
WO (1) WO2008111957A2 (en)

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US7661924B2 (en) * 2007-03-28 2010-02-16 General Electric Company Method and apparatus for assembling turbine engines
US8388308B2 (en) * 2007-10-30 2013-03-05 General Electric Company Asymmetric flow extraction system
FR2945331B1 (en) * 2009-05-07 2011-07-22 Snecma VIROLE FOR AIRCRAFT TURBOOMOTOR STATOR WITH MECHANICAL LOADING DUCKS OF AUBES.
FR2958694B1 (en) * 2010-04-07 2014-04-18 Snecma ENGINE COMPRESSOR, IN PARTICULAR AIRCRAFT TURBOJET ENGINE, EQUIPPED WITH AN AIR-TESTING SYSTEM
US20110274537A1 (en) * 2010-05-09 2011-11-10 Loc Quang Duong Blade excitation reduction method and arrangement
GB201015029D0 (en) * 2010-09-10 2010-10-20 Rolls Royce Plc Gas turbine engine
US9498289B2 (en) 2010-12-21 2016-11-22 Restoration Robotics, Inc. Methods and systems for directing movement of a tool in hair transplantation procedures
US9528391B2 (en) 2012-07-17 2016-12-27 United Technologies Corporation Gas turbine engine outer case with contoured bleed boss
US20140093355A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Extended indentation for a fastener within an air flow
JP6134628B2 (en) * 2013-10-17 2017-05-24 三菱重工業株式会社 Axial flow compressor and gas turbine
US10451084B2 (en) * 2015-11-16 2019-10-22 General Electric Company Gas turbine engine with vane having a cooling inlet
US10227930B2 (en) * 2016-03-28 2019-03-12 General Electric Company Compressor bleed systems in turbomachines and methods of extracting compressor airflow
US10443393B2 (en) * 2016-07-13 2019-10-15 Safran Aircraft Engines Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the seventh stage of a turbine
US10443392B2 (en) * 2016-07-13 2019-10-15 Safran Aircraft Engines Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the second stage of a turbine
US10934943B2 (en) 2017-04-27 2021-03-02 General Electric Company Compressor apparatus with bleed slot and supplemental flange
FR3074855A1 (en) * 2017-12-11 2019-06-14 Airbus Operations GRID FOR FORMATION OF AN INVERSION FLOW OF AN AIRCRAFT TURBOJET ENGINE
CN112228379B (en) * 2020-10-16 2022-11-22 中国航发沈阳发动机研究所 Air entraining pipe
CN114087028B (en) * 2021-11-12 2023-09-08 中国航发沈阳发动机研究所 Be suitable for adjustable stator inner ring bleed air structure
US11725530B1 (en) * 2022-05-20 2023-08-15 General Electric Company Offtake scoops for bleed pressure recovery in gas turbine engines
US11873737B1 (en) * 2022-07-22 2024-01-16 Pratt & Whitney Canada Corp. Flow deflector for aperture in gas turbine engine flowpath wall
US20240044288A1 (en) * 2022-08-02 2024-02-08 Pratt & Whitney Canada Corp. Porous cover for a takeoff port of a gas turbine engine
US12196141B2 (en) 2023-04-19 2025-01-14 Honeywell International Inc. Systems and methods with distributed bleed for gas turbine engine compressor stabilization

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Also Published As

Publication number Publication date
CN101595287B (en) 2013-10-09
GB0904122D0 (en) 2009-04-22
WO2008111957A2 (en) 2008-09-18
GB2454434A (en) 2009-05-06
DE112007002131T5 (en) 2009-07-16
US20090000306A1 (en) 2009-01-01
WO2008111957A3 (en) 2008-11-06
CN101595287A (en) 2009-12-02
GB2454434B (en) 2011-03-23
US8292567B2 (en) 2012-10-23

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